公开(公告)号：US20150226116A1

公开(公告)日：2015-08-13

申请号：US14429071

申请日：2013-09-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel W. Major ,  Gregory E. Reinhardt ,  Paul Thomas Rembish ,  Barry William Spaulding ,  Donald Summers

IPC: F02C3/073 ,  F02C7/20 ,  F02C7/36

CPC classification number: F02C3/073 ,  F01D17/162 ,  F01D25/243 ,  F02C7/20 ,  F02C7/36 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2260/31 ,  F05D2260/40311 ,  F05D2260/79 ,  Y10T29/49233

Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.

Abstract translation: 用于将风扇驱动齿轮系统模块固定在燃气涡轮发动机内的连接组件包括通过径向延伸的紧固件可拆卸地彼此固定的第一和第二构件。

公开(公告)号：US09964032B2

公开(公告)日：2018-05-08

申请号：US14429071

申请日：2013-09-12

Applicant: United Technologies Corporation

Inventor： Daniel W. Major ,  Gregory E. Reinhardt ,  Paul Thomas Rembish ,  Barry William Spaulding ,  Donald Summers

IPC: F02C3/073 ,  F02C7/20 ,  F02C7/36 ,  F01D25/24 ,  F01D17/16

CPC classification number: F02C3/073 ,  F01D17/162 ,  F01D25/243 ,  F02C7/20 ,  F02C7/36 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2230/70 ,  F05D2260/31 ,  F05D2260/40311 ,  F05D2260/79 ,  Y10T29/49233

Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.

公开(公告)号：US09863459B2

公开(公告)日：2018-01-09

申请号：US14692428

申请日：2015-04-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kelton Gallant ,  Barry William Spaulding

IPC: F16B21/18 ,  F16B41/00 ,  F01D25/24

CPC classification number: F16B41/002 ,  F01D25/246 ,  F05D2230/64 ,  F05D2250/281 ,  F16B21/183

Abstract: The present disclosure relates generally to a fastener lock for engaging a threaded fastener. The fastener lock defines a discontinuous circular opening therethrough with at least one extending tab extending into the discontinuous circular opening. When a threaded fastener is disposed in the discontinuous circular opening, the at least one extending tab engages the threads of the threaded fastener.

公开(公告)号：US10767555B2

公开(公告)日：2020-09-08

申请号：US15877077

申请日：2018-01-22

Applicant: United Technologies Corporation

Inventor： Daniel W. Major ,  Gregory E. Reinhardt ,  Paul Thomas Rembish ,  Barry William Spaulding ,  Donald Summers

IPC: F02C3/073 ,  F01D17/16 ,  F01D25/24 ,  F02C7/20 ,  F02C7/36

Abstract: A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.

公开(公告)号：US20180142620A1

公开(公告)日：2018-05-24

申请号：US15877077

申请日：2018-01-22

Applicant: United Technologies Corporation

Inventor： Daniel W. Major ,  Gregory E. Reinhardt ,  Paul Thomas Rembish ,  Barry William Spaulding ,  Donald Summers

IPC: F02C3/073 ,  F02C7/36 ,  F02C7/20 ,  F01D25/24 ,  F01D17/16

Abstract: A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.